GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 500,000 Max Cl/Cd: 52.26 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k2-il-500000-n5.txt Download as CSV file: xf-k2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.9369 0.07067 0.06723 -0.0479 1.0000 0.0118
-13.250 -0.9689 0.06148 0.05780 -0.0536 1.0000 0.0118
-13.000 -0.9935 0.05505 0.05116 -0.0563 1.0000 0.0118
-12.750 -1.0133 0.05012 0.04602 -0.0572 1.0000 0.0118
-12.500 -1.0291 0.04619 0.04188 -0.0570 1.0000 0.0118
-12.250 -1.0419 0.04293 0.03843 -0.0558 1.0000 0.0118
-12.000 -1.0518 0.04021 0.03553 -0.0541 1.0000 0.0119
-11.750 -1.0595 0.03791 0.03304 -0.0518 1.0000 0.0119
-11.500 -1.0655 0.03594 0.03091 -0.0491 1.0000 0.0120
-11.250 -1.0707 0.03423 0.02905 -0.0460 1.0000 0.0121
-11.000 -1.0759 0.03278 0.02745 -0.0424 1.0000 0.0121
-10.750 -1.0825 0.03155 0.02610 -0.0382 1.0000 0.0122
-10.500 -1.0827 0.03027 0.02468 -0.0350 1.0000 0.0122
-10.250 -1.0770 0.02896 0.02323 -0.0326 1.0000 0.0123
-10.000 -1.0682 0.02775 0.02188 -0.0307 1.0000 0.0124
-9.750 -1.0569 0.02663 0.02062 -0.0290 1.0000 0.0124
-9.500 -1.0456 0.02533 0.01922 -0.0272 1.0000 0.0126
-9.250 -1.0316 0.02429 0.01808 -0.0257 1.0000 0.0127
-9.000 -1.0077 0.02329 0.01700 -0.0262 0.9992 0.0128
-8.750 -0.9832 0.02241 0.01605 -0.0265 0.9983 0.0130
-8.500 -0.9577 0.02161 0.01518 -0.0270 0.9973 0.0132
-8.250 -0.9313 0.02085 0.01435 -0.0276 0.9963 0.0134
-8.000 -0.9043 0.02011 0.01355 -0.0282 0.9954 0.0136
-7.750 -0.8771 0.01941 0.01279 -0.0288 0.9947 0.0139
-7.250 -0.8239 0.01810 0.01135 -0.0297 0.9930 0.0144
-7.000 -0.7977 0.01749 0.01068 -0.0299 0.9919 0.0148
-6.750 -0.7708 0.01693 0.01005 -0.0303 0.9909 0.0151
-6.500 -0.7432 0.01635 0.00945 -0.0308 0.9898 0.0155
-6.250 -0.7147 0.01586 0.00895 -0.0315 0.9888 0.0161
-6.000 -0.6852 0.01545 0.00853 -0.0323 0.9877 0.0167
-5.750 -0.6552 0.01504 0.00810 -0.0332 0.9868 0.0175
-5.500 -0.6244 0.01463 0.00766 -0.0342 0.9859 0.0182
-5.250 -0.5931 0.01418 0.00720 -0.0354 0.9851 0.0190
-5.000 -0.5613 0.01381 0.00684 -0.0366 0.9844 0.0200
-4.750 -0.5294 0.01349 0.00651 -0.0378 0.9838 0.0212
-4.500 -0.5009 0.01317 0.00617 -0.0382 0.9826 0.0224
-4.250 -0.4732 0.01285 0.00587 -0.0384 0.9811 0.0241
-4.000 -0.4438 0.01260 0.00562 -0.0390 0.9796 0.0261
-3.750 -0.4134 0.01229 0.00535 -0.0398 0.9784 0.0288
-3.500 -0.3826 0.01204 0.00512 -0.0407 0.9773 0.0318
-3.250 -0.3514 0.01181 0.00491 -0.0416 0.9763 0.0358
-3.000 -0.3198 0.01157 0.00472 -0.0427 0.9755 0.0420
-2.750 -0.2875 0.01131 0.00453 -0.0439 0.9746 0.0516
-2.500 -0.2541 0.01100 0.00434 -0.0454 0.9739 0.0710
-2.250 -0.2193 0.01055 0.00413 -0.0473 0.9732 0.1202
-2.000 -0.1831 0.00990 0.00390 -0.0499 0.9729 0.2158
-1.750 -0.1460 0.00925 0.00369 -0.0527 0.9728 0.3224
-1.500 -0.1057 0.00843 0.00345 -0.0565 0.9732 0.4630
-1.250 -0.0646 0.00774 0.00340 -0.0601 0.9739 0.6169
-1.000 -0.0315 0.00769 0.00366 -0.0610 0.9731 0.6936
-0.750 0.0012 0.00772 0.00373 -0.0618 0.9705 0.7160
-0.500 0.0363 0.00754 0.00358 -0.0629 0.9626 0.7237
-0.250 0.0753 0.00725 0.00328 -0.0647 0.9522 0.7306
0.000 0.1108 0.00697 0.00299 -0.0658 0.9396 0.7362
0.250 0.1425 0.00683 0.00287 -0.0661 0.9227 0.7422
0.500 0.1832 0.00669 0.00269 -0.0684 0.9021 0.7508
0.750 0.2272 0.00660 0.00252 -0.0713 0.8565 0.7546
1.000 0.2514 0.00732 0.00249 -0.0699 0.6822 0.7573
1.250 0.2701 0.00807 0.00270 -0.0679 0.5520 0.7602
1.500 0.2931 0.00866 0.00285 -0.0670 0.4444 0.7631
1.750 0.3179 0.00922 0.00299 -0.0666 0.3411 0.7660
2.000 0.3448 0.00957 0.00311 -0.0665 0.2843 0.7684
2.250 0.3705 0.00992 0.00326 -0.0660 0.2331 0.7700
2.500 0.3965 0.01027 0.00344 -0.0656 0.1866 0.7717
2.750 0.4226 0.01062 0.00361 -0.0653 0.1459 0.7735
3.000 0.4492 0.01096 0.00379 -0.0650 0.1137 0.7754
3.250 0.4764 0.01123 0.00396 -0.0649 0.0929 0.7774
3.500 0.5041 0.01147 0.00413 -0.0649 0.0792 0.7796
3.750 0.5320 0.01172 0.00430 -0.0649 0.0652 0.7817
4.250 0.5866 0.01243 0.00478 -0.0648 0.0288 0.7855
4.500 0.6129 0.01276 0.00509 -0.0644 0.0216 0.7868
4.750 0.6393 0.01308 0.00541 -0.0640 0.0173 0.7881
5.000 0.6657 0.01341 0.00574 -0.0637 0.0151 0.7895
5.250 0.6922 0.01375 0.00609 -0.0633 0.0138 0.7911
5.500 0.7186 0.01413 0.00648 -0.0630 0.0129 0.7928
5.750 0.7453 0.01449 0.00688 -0.0627 0.0122 0.7944
6.000 0.7720 0.01486 0.00729 -0.0625 0.0116 0.7960
6.250 0.7986 0.01528 0.00773 -0.0623 0.0111 0.7978
6.500 0.8248 0.01580 0.00827 -0.0620 0.0106 0.7998
6.750 0.8512 0.01633 0.00883 -0.0618 0.0103 0.8015
7.000 0.8767 0.01682 0.00938 -0.0613 0.0101 0.8028
7.250 0.9014 0.01736 0.01000 -0.0607 0.0098 0.8039
7.500 0.9258 0.01795 0.01066 -0.0600 0.0096 0.8050
7.750 0.9498 0.01858 0.01136 -0.0593 0.0094 0.8063
8.000 0.9735 0.01925 0.01211 -0.0586 0.0092 0.8078
8.250 0.9971 0.01996 0.01290 -0.0578 0.0090 0.8093
8.500 1.0204 0.02070 0.01372 -0.0571 0.0089 0.8108
8.750 1.0434 0.02150 0.01460 -0.0563 0.0088 0.8123
9.000 1.0661 0.02235 0.01555 -0.0555 0.0087 0.8138
9.250 1.0883 0.02325 0.01654 -0.0547 0.0086 0.8153
9.500 1.1101 0.02418 0.01757 -0.0538 0.0085 0.8170
9.750 1.1312 0.02523 0.01872 -0.0529 0.0084 0.8187
10.000 1.1498 0.02645 0.02007 -0.0516 0.0082 0.8200
10.250 1.1653 0.02808 0.02190 -0.0499 0.0081 0.8211
10.500 1.1830 0.02926 0.02325 -0.0485 0.0080 0.8222
10.750 1.1996 0.03051 0.02470 -0.0469 0.0080 0.8234
11.000 1.2144 0.03194 0.02633 -0.0452 0.0079 0.8247
11.250 1.2267 0.03357 0.02819 -0.0432 0.0079 0.8261
11.500 1.2365 0.03537 0.03021 -0.0410 0.0078 0.8277
11.750 1.2425 0.03743 0.03253 -0.0384 0.0078 0.8295
12.000 1.2447 0.03968 0.03504 -0.0355 0.0078 0.8313
12.250 1.2394 0.04193 0.03752 -0.0316 0.0077 0.8330
12.500 1.2315 0.04451 0.04032 -0.0281 0.0077 0.8347
12.750 1.2177 0.04771 0.04377 -0.0248 0.0077 0.8361
13.000 1.2019 0.05131 0.04761 -0.0225 0.0077 0.8373
13.250 1.1801 0.05618 0.05274 -0.0219 0.0077 0.8385
13.500 1.1546 0.06297 0.05978 -0.0248 0.0077 0.8399
13.750 1.1176 0.07769 0.07483 -0.0380 0.0078 0.8411
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